Contoured class divider

ABSTRACT

In a preferred embodiment, a contoured class divider for dividing an aircraft cabin includes a panel positioned between an aft seat and a forward seat, the panel having an aft-facing convex contour closely matching an aft-facing contour of a seatback of the forward seat and configured to enhance space utilization. The contoured class divider may include an articulation system to articulate at least a portion of the panel from a first position (normal operation) to a second position (emergency landing). The contoured class divider may provide up to an additional 12 inches of space which can be used to reduce seat pitch (and thereby enhance passenger comfort) or increase the number of rows of seats on a given aircraft.

CROSS REFERENCES TO RELATED APPLICATIONS

This application is a continuation-in-part of and claims priority toU.S. patent application Ser. No. 15/153,104 entitled “Contoured ClassDivider” and filed May 12, 2016, which claims priority to U.S.Provisional Patent Application No. 62/317,706 filed Apr. 4, 2016, thecontents of each of which are incorporated by reference in theirentireties. The present disclosure is also related to PCT applicationnumber PCT/US16/32061 entitled “Contoured Class Divider” and filed May12, 2016, the contents of which is incorporated by reference in itsentirety.

BACKGROUND

The present disclosure relates to commercial aircraft multi-class cabinarrangements and how they can be efficiently separated from each other.One method to achieve division of the seat groups is by providing a harddivider between rows of seats attached to the aircraft seat tracks andan upper support element such as an overhead storage bin assembly orpassenger service unit (PSU) rail.

Head Injury Criteria (HIC) requirements are provided, for example, bythe Federal Aviation Administration (FAA) to establish standards inpassenger protection in passenger aircraft cabin design. Certain HICrequirements are set forth in 14 CFR 23.562, which is incorporatedherein by reference. The HIC requirements, for example, result inclearance requirements within a head impact zone to reduce likelihood ofpassenger concussion in the event of an emergency such as rapiddeceleration. Further, the requirements specify a measureable HIC numberresulting from, for example, a head impact against objects that arewithin the head impact zone of a passenger, such as a fore passengerseat or a partition. In this manner, should a passenger's head impact anobject such as the forward backrest of the fore passenger seat, theforce of the impact is absorbed at least in part through the backrestdesign.

Federal regulations also dictate certain standards for static loadhandling and dynamic load handling. 14 CFR 25.562 (incorporated hereinby reference) provides that seats and restraint systems must be able towithstand a 16G dynamic load. 14 CFR 25.561 (incorporated herein byreference) provides that other aircraft structures such as bulkheadsmust be able to withstand a 9G forward static load. It is understood inthe industry that if structures are spaced within one inch of oneanother, it must be demonstrated that the structures are capable ofsharing loads during normal use and emergency landing conditions. Due tothe complexity of the analysis, those skilled in the art of aircraftinterior components generally avoid placing components within one inchof one another. For this reason, a minimum spacing of one inch hasgenerally been maintained between bulkheads and seating systems (e.g.between a bulkhead and the aft surface of an aircraft seat).

SUMMARY OF ILLUSTRATIVE EMBODIMENTS

In one aspect, to optimize the usable space between cabin classes, acontoured class divider according to this application is specificallydesigned to nest into the volume behind the seat body following theprofile of the seatback while still allowing for adequate seatbackrecline. In some embodiments, the form of the divider allows the seatimmediately behind the contoured class divider to be located severalinches closer to the seat forward of it, thus increasing the opportunityfor increased seat pitch and passenger legroom in the cabin.

In one aspect, to increase passenger safety in the event of a rapiddeceleration (e.g., as would occur during an emergency landing) alocking mechanism is design to release to allow the partition to moveforwardly, increasing the clearance between the passenger and thedivider. The locking mechanism, in one example, may include a shear pinwhich remains in its locked position until it is subjected tolongitudinal acceleration associated with an emergency landing. Underthose conditions the deceleration force experienced by the divider issufficient to overcome the pin static shear force and the divider movesforwardly.

In another aspect, to increase passenger safety in the event of rapiddeceleration, a contoured class divider according to this applicationincludes at least one energy absorbing zone to absorb the energy of ahead impact in the event of an emergency situation. In one example, anenergy absorbing zone includes one or more structurally weakenedportions designed to deform or break as a result of a threshold dynamicload. In other examples, the energy absorbing zone includes one or moreportions embedded with energy absorbing material. The energy absorbingmaterial may be foam. In further examples, the energy absorbing zone isdesigned to deform in a predetermined manner.

In a further aspect, the placement of a class divider panel within lessthan one inch of a seat or restraint system is facilitated by providinga known impact or interaction points between the divider and seat back.Impact protrusions or other design elements described herein may provideknown points at which the divider will impact the seat, which will inturn simplify and make practical the calculations necessary to show thatthe divider and seat are able to withstand the projected load sharing inan emergency landing.

These and other objects and advantages of the embodiments describedherein may be achieved, in some implementations, by providing acontoured class divider that includes a curved panel. The curved panelmay be mounted into seat tracks T behind a selected row of seats. Thecurve of the panel may closely correspond to the shape of the back ofthe selected row of seats and may nest into the volume behind theseatback while still allowing for adequate seatback recline. Morespecifically, a contoured class divider may be provided for dividing anaircraft cabin according to a predetermined class arrangement andincluding a divider panel having a contour closely matching a contour ofa forward-positioned seatback and adapted for being positioned inclosely, spaced-apart relation to the seatback for providing additionalspace aft of the seat. At least one leg may be provided for supportingthe panel about an aircraft cabin deck. A viewing window may be formedin the panel for providing the ability of a flight attendant to observeareas of the cabin forward or aft of the divider.

In one non-limiting illustrative example, a contoured class divider fordividing an aircraft cabin may include a panel positioned between a aftseat and a forward seat, the panel having an aft-facing convex contourclosely matching an aft-facing contour of a seatback of the forward seatand configured to provide a gain of space forward of the aft seat; andat least one foot inserted into a seat track of the aircraft cabin; anarticulation system to articulate the panel from a rearward position toa forward position and to increase the space between the divider and theseats immediately aft thereof (or, alternatively, permit those seats tobe moved forward and, in some configurations, thereby enable anadditional row of seats to be disposed on the airplane); and at leastone connector that connects a top end of the panel and an overheadstructural element of the aircraft cabin.

In one non-limiting illustrative example, a contoured class divider fordividing an aircraft cabin includes a panel positioned between a aftseat and a forward seat, the panel having an aft-facing convex contourclosely matching an aft-facing contour of a seatback of the forward seatseatback and configured to provide increased space between the dividerand the seats immediately aft thereof (or, alternatively, permit thoseseats to be moved forward and, in some configurations, thereby enable anadditional row of seats to be disposed on the airplane), and a headimpact zone configured to limit an impact shock between a passenger headand the panel; and at least one foot inserted into a seat track of theaircraft cabin; an articulation system to articulate the panel from arearward position to a forward position and to increase the gain ofspace forward of the aft seat; and at least one connector that connectsa top end of the panel and an overhead structural element of theaircraft cabin.

In one non-limiting illustrative example, an apparatus to divide classsections within a commercial aircraft is presented. The apparatus mayinclude a divider panel positioned between an aft seat and a forwardseat, the panel having an aft-facing convex contour closely matching anaft-facing contour of a seatback of the forward seat seatback andconfigured to provide increased space between the divider and the seatsimmediately aft thereof (or, alternatively, permit those seats to bemoved forward and, in some configurations, thereby enable an additionalrow of seats to be disposed on the airplane). The apparatus may includeat least one impact protrusion configured to be the initial point ofimpact if the forward seat makes contact with the panel. The panel mayinclude at least one foot inserted into a seat track of the aircraftcabin. The apparatus may include an articulation system to articulatethe panel from a rearward position to a forward position and vice-versa,allowing the gain of space forward of the aft seat; and at least oneconnector that connects a top end of the panel and an overheadstructural element of the aircraft cabin.

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete appreciation of the innovations and many of theattendant advantages thereof will be readily obtained as the samebecomes better understood by reference to the following detaileddescription when considered in connection with the accompanyingdrawings, where:

FIG. 1 is a forward perspective view of an aircraft cabin, showing anexample contoured class divider and forward-positioned seats;

FIG. 2 is a side view of an example contoured class divider andforward-positioned seat;

FIG. 3 is an aft perspective view of an example contoured class divider;

FIG. 4A is a forward perspective view of an example contoured classdivider;

FIG. 4B is a forward perspective view of another example contoured classdivider;

FIG. 5 is a forward perspective view of an example set of two side classdividers and a center class divider;

FIG. 6 is a partial plan view of an aircraft cabin showing an exampleplacement of side contoured class dividers and a center class divider;

FIGS. 7A-7I illustrate side views of example contoured class dividersshowing embodiments of articulation systems;

FIGS. 8A-8C illustrate views of an example locking system for locking aposition of the contoured class divider upon articulation;

FIGS. 9A-9C are forward perspective views of example contoured classdividers with a head impact zone protection feature;

FIGS. 9D-9E are forward perspective views of an example contoured classdivider with another head impact zone protection feature;

FIGS. 10A-10C illustrate example impact protrusion configurations forestablishing an impact zone between a contoured class divider andforward-positioned seats; and

FIG. 11 is a side view of an example contoured class divider designedfor affixing to at least one forward-positioned passenger seat.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

Referring now specifically to FIG. 1 of the drawings, a contoured portside class divider 10 is positioned directly behind a row of two firstor business class passenger seats S such as are conventionally found incommercial aircraft cabins. Such cabins typically include bothstructural and decorative panels and overhead stowage bins for passengerluggage and other items. The divider 10 may include a fixed, rigidmonument in the form of a panel 12 attached to floor-mounted seat tracksT and the overhead stowage bin B of the aircraft cabin. The exactattachment configuration may be dependent upon aircraft type and cabinconfiguration. The contoured port side class divider 10 may include anattendant viewing window 14. The attendant viewing window 14, forexample, may be inset into an outer corner of the upper part of thepanel 12 that can be defined by the airlines' cosmetic specifications.The window 14 may be clear or automatically dimmable. The divider 10 mayseparate a premium cabin area (e.g. first class or business class) fromanother cabin area (e.g. coach class seating).

Referring to FIG. 2, in some embodiments, a contoured class divider 200optimizes use of the space behind the seat 202 that is normally notutilized or inefficiently utilized. By forming a panel 204 that followsthe contour of the back of seat 202, the passenger in the seats aft ofthe divider may be provided enhanced space while also enhancing theability of the seat and divider system to meet Head Impact Criteria(HIC) requirements. As shown, the panel 204 in the rear-facing directionis generally concave with a lower section 204 a that is relatively flatin order to accommodate optionally supplied pockets 22 (illustrated inFIG. 1) for use by occupants of aft-positioned seats.

Returning to FIG. 1, three pockets 22 correspond to three main cabinseats (not shown) positioned immediately aft of the pockets. Thecontoured divider enables the aft seats (not shown) to be moved forwardone to six inches towards the divider 10, more preferably three to fiveinches toward the divider 10 and in a currently preferred embodimentabout four inches toward the divider 10. A panel 12, in someembodiments, is elevated off the floor by support legs 16, 18, allowingfor stowage of passenger items under the seats S forward of the divider10 by the passengers in the three main cabin seats.

The legs 16, 18, in some embodiments, are bowed rearwardly in a convexmanner. This may provide additional clearance between the legs 16, 18 ofthe divider 10 and the rear legs of the seat. Such a configurationallows the bottom of the divider 10 to offset further forward and nestcloser into the back of the seat S in front, thus, increasing the livingspace for the passengers immediately aft of the divider. It may alsoprovide enhanced resistance to deflection of the divider 10 in the aftdirection, as might occur if the divider is impacted by excessiverecline of the seatback of the seat S or 202 or if forced rearwardly bya passenger. In alternative configurations, the legs 16, 18 are bowedforwardly in a concave manner (not shown). This configuration has theadvantages that the legs 16, 18 generally follow the contour of the rearlegs of the seats 202, provide more ingress and egress foot clearancefor passengers in the three main cabin seats, and enhanced resistance toforward deflection of the divider.

Referring to FIG. 3, a top end of the divider 10 may be secured againstdeflection by a connector 20 that attaches the divider 10 to an overheadstructure below the bins B. Therefore, both the top and bottom of thedivider 10 may be secured against movement. In the circumstance of astationary mount of the divider 10, sufficient space may be providedbetween the panel 12 and the seats S to allow for the conventionalamount of seatback recline. The panel 12 may also provide additionallegroom for the occupants of seats aft of the divider 10 through boththe contoured curve and the opening provided by the legs 16, 18.

In some embodiments, the legs 16, 18 are coupled to the divider by forcedistributing flanges 24 and 26. These flanges disperse the loadtransferred between the legs and panel 12 such that the panel can be ofa relatively lightweight construction with either modest or nostructural reinforcement in the region of the leg 16 and 18.

Returning to FIG. 2, in some embodiments an upper portion 204 b of thepanel 204 is generally straight and arranged in a substantially verticalorientation when in the normal operative position (illustrated in dottedlines). The upper portion 204 b may include a connector (notillustrated), such as connector 20 of FIG. 1, to secure the contoureddivider panel 200 to an overhead structure, such as overhead storagebins. The contoured class divider 200, in some embodiments, is designedto automatically move to a forward position (shown in solid lines) in anemergency situation involving substantial deceleration or otheremergency circumstance. For example, to provide additional headclearance for aft-positioned passengers in the event of an emergencylanding, the contoured class divider 200 may be configured toautomatically actuate from its rearward position (dashed lines) to theforward position (solid lines). Various configurations designed toenable automatic deflection of the contoured class divider position aredescribed in detail below.

In another example, the contoured class divider 200 may be positioned inthe forward (solid line) position during take-off and landing, and inthe rearward (dashed line) position in-flight. For example, asillustrated in dashed lines, the passenger seat 202′ may only haveclearance to move to a rearward position (illustrated in dashed lines)when the contoured class divider is positioned in the rear (dashed line)position. In this situation, the positioning of the contoured classdivider 200 may be actuated by a passenger or crew member. In oneexample, a passenger may cause the contoured class divider 200 toactuate to a rearward position by selecting a control such as theconventional passenger seat back recline control. In another example, acrew member may have access to a control positioned proximate theoverhead bin (e.g. on the underside of the bin adjacent the slot intowhich a connector extends, or inside the bin).

Referring now to FIG. 5, a set of contoured dividers, in someimplementations, include a port divider 30, a center divider 50, and astarboard divider 70. Port divider 30, as illustrated, includes a panel32. The port divider 30, in some examples, may be attached tofloor-mounted seat tracks via legs 36, 38 and to the overhead stowagebin of the aircraft cabin via connector 42 in a manner similar to thatdescribed in relation to FIGS. 1 and 2. The connector 42 preferablymates with the overhead bin in a manner that permits the panel toactuate between the forward and rearward positions. The exact attachmentconfiguration, in some embodiments, is dependent upon aircraft type andcabin configuration. The divider 30 may include an attendant viewingwindow 34 that is inset into an outer corner of the upper part of thepanel 32 that permits crew to view through the divider 30 when standing.This provides privacy for the seated passengers while improvingvisibility of crew members. The window 34, in some examples, may beclear or have electronically adjustable opacity, tint, or reflectivity.

The panel 32, in the illustrative embodiment, is generally concave inthe rear-facing direction with a lower section 32 a that is relativelyflat. The lower section 32 a, for example, may be designed toaccommodate pockets 40 for use by occupants of aft-positioned seats. Theprofile of the top end of the panel 32, in the illustrative embodiment,is curved to fit a fuselage and storage bin configuration different thanthat shown in FIGS. 1-4. The port divider 30 may be secured againstdeflection by a connector 42 that attaches the port divider 30 to anoverhead structure (not shown) such as the underside of a storage bin.

The center divider 50, in some embodiments, includes a panel 52. Thecenter divider 50, in some examples, may be attached to floor-mountedseat tracks via legs 56, 58, 60, and 62 and to the overhead stowage binof the aircraft cabin by connectors 64, 66 in the manner discussedabove. The center divider 50 may include, for example, an attendantviewing window 54 that is inset into an outer corner of the upper partof the panel 52 that may have the properties discussed above. Legs 56,58, 62, and 62 may be bowed rearwardly as shown and as described above.The panel 52 in the rear-facing direction, in the illustrativeembodiment, is generally concave with a lower section 52 a that isrelatively flat. The lower section 52 a, for example, may be designed toaccommodate pockets 68 for use by occupants main cabin seats positionedimmediately aft of the divider 50. The profile of the top end of thepanel 52, in the illustrative embodiment, is curved to fit storage binsmounted on the center aisle above the center passengers. The centerdivider 50 may be secured against deflection by connectors 64, 66 thatattach the center divider 50 to an overhead structure, not shown. Theconnectors preferably permit the divider to move between a rear positionand forward position, as discussed above.

A starboard side divider 70, in some implementations, may be attached tofloor-mounted seat tracks via legs 76, 78 and to the overhead stowagebin of the aircraft cabin via connector 82 in a manner similar to thatdescribed above. The starboard divider 70 may include an attendantviewing window 74 that is inset into a corner of the upper part of thepanel 72 that may have the properties and functionality discussed above.The panel 72 in the rear-facing direction, in the illustrativeembodiment, is generally concave with a lower section 72 a that isrelatively flat. The lower section 72 a, for example, may be designed toaccommodate pockets 80 for use by occupants of passengers in the seatsimmediately aft of the divider 70. The profile of the top end of thepanel 82, in the illustrative embodiment, is curved to fit a storage binconfiguration different than that shown in FIGS. 1-4. The connector 82preferably permits the divider to move between a rear position andforward position, as discussed above.

As shown in FIG. 6, the port side, center and starboard side classdividers 30, 50 and 70, in an illustrative embodiment, are positioned todivide an aircraft cabin into separate classes. The dividersadvantageously form a divider system wherein the starboard, center andport dividers are positioned a varying longitudinal positions (fore/aft)in the cabin. This helps accommodate galley and other structures whichare often disposed in the center of the cabin and can require the centercolumn of seats to be shifted rearwardly relative to the starboard orport columns of seats.

FIG. 7A is a side view of an example contoured class divider 700 shownthe rearward position. The contoured class divider 700, for example, maybe similar to the contoured class divider 10 illustrated in FIG. 4A. Theclass divider 700 includes a panel section 706 positioned between astorage bin region 714 and at least one leg 708, and a foot or floormount 710. The floor mount 710, for example, may be a portion of theleg(s) 708 that is inserted in floor-mounted seat tracts 712. Forexample, as illustrated in FIG. 4A, the contoured class divider 700 mayinclude a total of two legs 708 (e.g., such as legs 16 of class divider10) and two feet 710. The passenger seat 704, as illustrated, may movefrom a upright position (illustrated in solid lines) to a reclinedposition (illustrated in dashed lines) where a seatback region 704 a ofthe passenger seat 704 is nested proximate a curved area of thecontoured class divider 700 while the seat is in a reclined position.Although illustrated as being positioned a distance away from thecontoured class divider 700, in other embodiments, the contoured classdivider 700 may be designed for load sharing between the passenger seat704 and the panel section 706. In such configurations, the distancebetween the seat and the divider in certain operative configurations isless than one inch.

FIG. 7B is a side view of the example contoured class divider 700 in arearward (solid lines) and forward (dashed line) positions. The seat 704is shown in the upright or take-off taxi and landing (TTOL) position.The contoured class divider 700, in some embodiments, includes thearticulation system 702 to articulate the divider 700 from a rearwardposition (illustrated in solid lines) to a forward position (illustratedin dashed lines). The articulation system includes a pivotable or hingedfloor mount 702 a and an upper connector 702 b that moves between aforward and a rearward position. In the forward position, the spacebehind the forward positioned passenger seats, such as the passengerseat 704, may be minimized such that the divider 700 more readily meetsthe FAA's Head Injury Criterion (HIC) requirements for the passengerseats immediately aft the contoured class divider 700. While in theforward position (dashed lines), for example, increased space between aset of aft passenger seats (not illustrated) and the contoured classdivider 700 may be outside of a conventional head path and impact zone(e.g., range of typical sized passenger head movement during anemergency deceleration). While in the rearward position (solid lines),in some implementations, the space aft the passenger seat 704 isadequate to provide clearance for conventional range of seatback reclinefor the passenger seat 704. For example, the forward position (dashedlines) can be used during a taxi takeoff landing (TTOL) phase or anemergency situation, e.g. anticipated impact, anticipated ditching,anticipated forced landing, while the rearward position can be usedduring a cruise phase. In another example, the divider may be placed inthe forward position (dashed lines) only in emergency circumstancesonly.

The articulation of the contoured class divider 700 from the rearwardposition (solid lines) to the forward position (dashed lines), in someimplementations, is configured to increase seating capacity and spacefor other cabin amenities while conforming to HIC requirements. Thecontour and/or articulation of the contoured class divider 700 mayenable the main cabin seats positions immediately aft the contouredclass divider 700 to be moved forward up to an amount roughly equal toor slightly greater than the amount of recline available on the forwardseat 704 inches (towards the contoured class divider 700) due to theincreased clearance provided by the contour and/or articulation of theclass divider 700. This may in many cabin configurations enable theinsertion of an additional row of main cabin and/or premium cabin seats.Alternatively or additionally, the space savings provided by the classdivider may alternatively be utilized to improve passenger comfort, asby enlarging the living space of for the passengers seated immediatelyaft of the divider or enlarging the living space in a number of rows(e.g., by increasing the seat pitch in the premium cabin, the forwardportion of the main cabin, or the rear portion of the main cabin)without reducing the number of seats on the aircraft. Seat pitch is thedistance between like points on seats juxtaposed fore and aft of oneanother.

In other embodiments, the divider 700 provides 1-12 inches of additionalclearance, 2-10 inches of additional clearance, 3-9 inches of additionalclearance, 4-8 inches of additional clearance, 5-7 inches of additionalclearance or about six inches of additional clearance. As discussedherein below, up to an additional inch of clearance may be provided bypositioning the seat and divider in close proximity (less than one inchapart) such that they share loads during normal operation and/oremergency landings.

The articulation system 702, in some implementations, includes at leastone pivot mechanism 702 a to enable articulation of the contoured classdivider 700 from the rearward position (solid lines) to the forwardposition (dashed lines), and vice-versa, via a rotation or pivoting ofat least the panel 706 of the contoured class divider 700 between therearward and forward positions. The at least one pivot mechanism 702 acan be placed at a predetermined position on the contoured class divider700, in one example, to maximize the additional clearance generated bythe articulation of the contoured class divider 700 from the rearwardposition (solid lines) to the forward position (dashed lines). Asillustrated, for example, the at least one pivot mechanism 702 a (suchas a rotatable pin connection) can be placed on the leg(s) 708 at toppart of the foot 710. The at least one pivot mechanism 702 a forexample, may be configured to rotate the panel 700 around a rotationaxis substantially parallel to a floor of the aircraft cabin, asillustrated in FIG. 7B, providing a rotation range A of the contouredclass divider 700. The positioning of the pivot mechanism 702 a may insome embodiments dictate the contour of the divider in that the divideris shaped or contoured to closely follow the contour of the seat back.The rotation range A may be about 1-15 degrees, about 2-14 degrees,about 3-13 degrees, about 4-12 degrees, about 5-11 degrees, about 6-10degrees, about 7-9 degrees or about 8 degrees.

In some embodiments, the articulation system 702 further includes alocking mechanism 702 b for locking the contoured class divider 700 ineither the rearward position (solid lines) or the forward position(dashed lines). The locking mechanisms are discussed in greater detailbelow in relation to FIGS. 8A-C.

As mentioned above, the divider may be positioned in the rearwardposition at all times until an emergency landing occurs. Thedecelerative force of the emergency landing moves the divider to theforward position without interfering with the seat because the seat willbe in the TTOL position during an emergency landing. This configurationadvantageously provides full recline for the seat forward of the divider(in the first, business or premium cabin) while provide theaforementioned amounts of additional clearance.

In an alternative embodiment, the divider is routinely articulatedbetween the forward and rearward positions by crew members. Forinstance, after reaching cruising altitude the crew may move the dividerto the rearward position. In preparation for TTOL, the crew may move thedivider to a forward position.

FIG. 7C depicts the functionality of the seat when the divider is in therearward position. The seat 704 may fully recline in the depictedembodiment without coming within one inch of the class divider, thusobviating the need to design the seat and divider to share loads. Theseat will be placed in the upright position during TTOL.

In some implementations, a contoured class divider 720, as illustratedin FIG. 7C, includes a panel section 722 positioned between the storagebin region 714 and at least one leg 724, and a foot 728. The foot 728,for example, may be a portion of the leg(s) 724 that is inserted infloor-mounted seat tracts 712. The panel 722 may be divided in an uppercurved region 722 a and in a lower straight region 722 b. The passengerseat 704, as illustrated, may move from a forward position (illustratedin solid lines) to a rearward position (illustrated in dashed lines)where a seatback region 704 a of the passenger seat 704 is nestedproximate the upper curved region 722 a of the contoured class divider720. Although illustrated as being positioned a distance away from thecontoured class divider 720, in other embodiments, the contoured classdivider 720 may be designed for load sharing between the passenger seat704 and the upper curved region 722 a (e.g. as where the divider andseat are spaced less than one inch away from each other). Asillustrated, the contoured class divider 720 is disposed between theseat tracts 712 of the cabin area and the bin region 714. In otherimplementations, the contoured class divider 720 may be fixed to otherupper cabin area structures.

FIG. 7D shows an alternative embodiment in which the pivot point ismid-way up the panel (as opposed to at the floor mount). Thearticulation system 726, in some implementations, includes at least onepivot mechanism 726 a to enable articulation of the contoured classdivider 720 from the rearward position (solid lines) to the forwardposition (dashed lines), and vice-versa, via a rotation of at least theupper panel region 722 a of the contoured class divider 720. The atleast one pivot mechanism 726 a can be placed at a predeterminedposition on the contoured class divider 720, in one example, to maximizea gain of space generated by the articulation of the contoured classdivider 720 from the rearward position (solid lines) to the forwardposition (dashed lines). As illustrated, for example, the at least onepivot mechanism 726 a can be placed at approximately the height of anarmrest 704 b of the passenger seat 704 (or mid-back region of thepassenger therein).

The at least one pivot mechanism 726 a for example, may be configured torotate the upper panel region 722 a around a rotation axis substantiallyparallel to a floor of the aircraft cabin, as illustrated in FIG. 7D,providing a rotation range B of the contoured class divider 720. Therotation range B may be about 2-20 degrees, about 5-15 degrees, about7-12 degrees or about 10 degrees.

This configuration provides the advantage that the pivoting or rotatingmass is reduced. This may permit the use of a higher strength (andheavier) panel construction or a lighter weight or lower strengthconnector mechanism. The mid-range positioning of the pivot mechanism726 a, for example, may be configured to lessen a load on the pivotmechanism 726 a as opposed to the embodiment illustrated in FIG. 7Awhere the pivot mechanism 702 a is located near the cabin floor.Moreover, this arrangement may more fully optimize usage of the spaceimmediate aft of the seat base in the divider is more closely spaced tothe lower portion of the seat even when the divider is in the rearwardposition. In addition, the rotation of the upper panel section 722 aaround the axis of rotation provided by the pivot 726 a allows the lowerpanel section 722 b to remain fixed, avoiding interference of thearticulation of the contoured class divider 720 with items that may beplaced below the panel 722 such as carry-on bags. An example reclinerange may be observed in the difference of position between thecontoured class divider 720 in the forward position (dashed lines) andin the rearward position (solid lines).

FIG. 7E illustrates a full height divider that prevents the passengersaft of the divider from placing their luggage under the seats 704. Thecontoured class divider 730, for example, may be similar to thecontoured class divider 10 illustrated in FIG. 4A. This embodimentenhances privacy by more completely separating the main cabin from thepremium cabin. This embodiment also provides for the storage of crewluggage, aircraft supplies and/or emergency equipment a cabinet orlocker positioned in the gap just forward of the panel and behind therear seat legs. The cabinet or locker (not shown) may be integrallyformed with or rigidly attached to the panel. The recline of the seat isshown in dashed lines.

FIG. 7F shows the panel of FIG. 7E articulated between a rearwardposition and forward position. The seat 704 is shown in the TTOLposition. As discussed above, the seat and divider may be placed closertogether (within one inch) if the divider and seats are configured toshare loads.

All of the functionality and features described above apply equally tothe embodiment shown in FIGS. 7E-7F. In some embodiments, a topconnector of an articulating contoured divider panel, such as theconnector 20 illustrated in FIG. 4, is designed to interoperate with alocking system. The locking system, in some embodiments, is configuredto lock the articulating contoured divider panel after articulation ofthe contoured class divider panel from a forward position to a rearwardposition or vice versa. In some embodiments, the locking system may beconfigured to automatically unlock in the event of a rapid decelerationevent to allow articulation from a present position to a forwardposition, moving the panel away from potential impact with aftwardlypositioned passenger seats.

FIGS. 7G, 7H and 7I depict one embodiment which is design to “use” thelast inch of clearance which is normally reserved to space apartcomponents such that they do not have to be designed to share loadsduring normal use and/or emergency landings. The upper portion 752 ofthe panel has less curvature than the seat such that it will have aknown point of impact 748/758 with the seat 704. The known point ofimpact 748/758, for example, can simplify load sharing simulations inthe circumstance of the dynamic load of the panel section 742 meetingthe passenger seat 704 in the event of an emergency situation. This mayenable the divider to be placed up to an inch closer to the seat 704,thereby providing an extra inch of clearance which may be utilized inthe manner described above. All of the functionality and featuresdescribed above apply equally to the embodiment shown in FIGS. 7G-7I.

FIGS. 8A-8C illustrate a locking system 800, according to certainaspects of the disclosure. The locking system 800, in some embodiments,is designed to automatically move an articulating contoured classdivider panel into the forward position from a rearward position whenthe aircraft cabin experiences a deceleration above an emergencydeceleration threshold. The emergency deceleration threshold cancorrespond, in some examples, to a deceleration generated by a forcedlanding or turbulences and can be between 5 g-force (G) and 20 G, andparticularly between 7 G and 13 G, and in some embodiments around 9 G.

The locking system 800, in some embodiments, includes a body 810 affixedto an overhead stowage bin (such as bin B illustrated in FIG. 1) orother structure above the passenger seats, a channel 812 in the housing810, and a shear pin 814 inserted in a rounded end 816 of the channel812 on one side and affixed to the contoured class divider panel onanother side (e.g., such as the connector 20 of FIG. 1). The channel812, as illustrated, includes enlarged ends 816 connected by a narrowerchannel region 812. The channel 812 can have a curved shape with aminimum width D, smaller than a diameter of the shear pin 814 such thatthe pin 814 is prevented from travel along the channel 812. The channeldimensions and friction coefficients are selected configured such that apredetermined force corresponding to the emergency decelerationthreshold will move the shear pin 814 from the first end 816 a to thesecond end 816 b by causing the material of the housing 810 surroundingthe channel 812 to deform. In selected embodiments, the shear pin is asingle use item and must be replaced after it is actuated because duringactuation the pin and/or body deform or have material sheared off theirsurface(s). After that occurs, the locking system 800 may no longeractivate at the same predetermined force.

In other implementations (not shown) the body permits the pin to moveaxially from the first end 816 a and to the second end 816 b via manualactuation by a cabin attendant. For example, to prepare for TTOL, thecabin attendant may retract a spring-loaded pin downwards out of anaperture in the housing, articulate the contoured class divider from arearward position to an upright position, and shift the pin upwards tolock it within a corresponding aperture of the housing. In otherembodiments, a manual latch mechanism may releasably retain the pin inthe two desired positions. The manual latch may be actuated by a handledisposed on the underside of the overhead bins. The latch and handle maybe connected via a cable.

Returning to the embodiment depicted in FIGS. 8A-8C, when thedeceleration generated by the emergency is higher than the emergencydeceleration threshold, the deceleration generates a force on thearticulating contour class divider panel that overcomes thepredetermined force, i.e. the force required to overcome the frictionbetween the channel 812 and the pin 814. The force generated on thepanel 12 slides the pin 230 along the channel 812 and articulates thecontoured class divider 10 from the inclined position and to the uprightposition. The force generated by the panel during deceleration is afunction of its mass and, to a lesser extent, the angular range ofmotion through which the pin travels. Depending on the density of thepanel, the pivot point may be moved mid-way up the divider to providethe desired predetermined force.

When the deceleration generated by the emergency is lower than theemergency deceleration threshold, the deceleration generates a force onthe articulating contoured class divider panel that is too weak toovercome the predetermined force, and the pin 814 cannot slide along thechannel 812. The pin 814 stays at proximity of the first end 816 a andthe contoured class divider panel is maintained in the rearwardposition.

In other embodiments (not shown), a spring-loaded latch is used toretain the pin in a the rearward position until the spring latchingforce is overcome by the predetermined force, at which time the pinmoves forward and its received and retained by another latch. In anothervariation the pin is permanently biased in the rearward direction.During deceleration the pin moves forward and when it reaches the frontof the channel it is retained and locked into place with a latch. Instill other embodiments, a spring may forwardly bias the pin which isheld in the rearward position by a latch. A solenoid may release the pinwhen an accelerometer detects a predetermined amount of deceleration. Atthat time the spring moves the pin forward in the channel and anotherlatch receives and retains the pin at the forward end of the channel. Instill further embodiments, electro-magnets may be used to hold the pinin place and/or repel a magnetic pin in the desired direction when anaccelerometer detects a predetermined amount of deceleration.

In some implementations, an articulating contoured class divider lockingsystem is designed to provide a fixed position panel except in the eventof an emergency. The fixed position panel may be configured to withstanda static load meeting or exceeding a dynamic load threshold. Uponexceeding the dynamic load threshold (e.g., indicative of an emergencydeceleration condition or other abrupt force), the locking system mayrelease to provide additional clearance for passengers and to avoidpassenger injury. In an illustrative example, the locking system may bedesigned to support static loads of 9 G while remaining in lockedposition. In the event of a dynamic load of about 16 G or greater,however, the primary locking mechanism of the locking system willrelease, and the panel will move into a secondary locking position, thusdissipating the inertial load by allowing the panel to shift forward ina controlled manner. For example, in some embodiments, the lockingsystem can automatically articulate the contoured class divider from theinclined position to the forward position when a deceleration generatedby an emergency, e.g. a series of turbulences, a forced landing, asudden braking, or other accident.

A contoured class divider, in some implementations, may varysubstantially in weight depending upon a deployment configuration. Forexample, the contoured class divider may be configured to hold one ormore video monitors, pockets filled with reading materials or otherpassenger convenient items, and/or passenger storage area. In aparticular example, a baby bassinette or other child seatingconfiguration may be suspended from the contoured class divider. Inthese circumstances, it may be desirable to move the pivot point up tothe middle of the panel as shown in FIG. 7D. Moreover, a purelymechanical solution for releasing the contoured class divider from itsrearward position to an emergency forward position may lack a desiredlevel of precision due to the variability of static weight on thecontoured class divider in various applications. In such embodiments oneof the electrically triggered mechanisms may be used to actuate thecontoured class divider from its in-flight rearward position to theemergency forward position. In one example, a signal from anaccelerometer may release a latching mechanism, allowing the contouredclass divider to shift forwards under the bias of a spring. The signal,for example, may be received from an accelerometer in the seat,proximate the locking system in the overhead bin, or in the cockpit.

Turning now to FIGS. 9A-9E, a contoured class divider may be designedwith weakened structural integrity within a head impact zone to furtherprotect passengers seated to the aft of the contoured class divider inthe event of an emergency landing. FIGS. 9A through 9C illustrateforward perspective view of embodiments of contoured class dividers withan enhanced head impact zone 904 for increased passenger safety.Particularly, the head impact zone 904 can be configured to limit a headimpact shock between a head of the passenger and the panel of thecontoured class divider through use of one or more energy absorbingzones having a predetermined location to face the head when thepassenger is in a brace position, e.g. the head on the knees of thepassenger.

Turning to FIG. 9A, a series of energy absorbing zone(s) 910 of acontoured class divider 900 can each include a core having slots cuttherein and covered by a fabric 912, such as a stretched tissue. Thefabric 912, in some examples, can have a similar appearance, texture,and or color as the surrounding surface of the contoured divider panel.In another example, the fabric 912 may be stretched to cover a widerportion of the contoured class divider panel 902 including the energyabsorbing zone(s) 910. In a particular example, the fabric 912 may bepositioned above a set of pockets 914 and up to the upper region of thepanel 902 interfacing with the storage bins or other ceiling structure(not illustrated), as well as across a full width of the contoureddivider panel 902. The fabric 912, in some embodiments, can have apredetermined surface tension sufficiently high to have a rigid surfaceappearance but sufficiently low to deflect when the head impact shockhappens. Alternatively, the panel 902 may be composed of layeredmaterials such that one or more interior layers of panel material isremoved at the energy absorbing zone(s) 910 and an exterior layer of thepanel 902 is intact across the energy absorbing zone(s) 910.

Turning to FIG. 9B, in some embodiments, each energy absorbing zone 910of a contoured class divider 920 includes perforations or otherapertures or cavities in the panel core material to weaken thestructural integrity of a contoured divider panel 922 at the energyabsorbing zone(s) 910. For example, each energy absorbing zone 910, asillustrated, may include a number of slots 916 machined on the panel 922to weaken the panel 922. Further, a material such as stretched tissue,as discussed in relation to FIG. 9A, may be positioned, in someimplementations, to cover at least the energy absorbing zone(s) 910 tomask the perforations, apertures or cavities in the panel 922.

Turning to FIG. 9C, as illustrated in relation to a contoured classdivider 930, in some embodiments, each energy absorbing zone 910 of acontoured class divider 920 includes a cushioning material 934 replacingor partially replacing the panel material of a contoured panel 932. Thecushioning material 934, for example, can include a foam material, amesh material, and/or a flexible material forming a plurality of pocketsfilled with air and/or gel. Further, a material such as stretchedtissue, as discussed in relation to FIG. 9A, may be positioned, in someimplementations, to cover at least the energy absorbing zone(s) 910 tomask the cushioning material 934 inserts.

Alternatively, the head impact zone 904, in some implementations, can beconfigured to avoid contact between the passenger and the contouredpanel. For example, the head impact zone 904 can include individualrecesses (not illustrated) sufficiently curved forwardly to avoidcontact between the head of the passenger and the contoured classdivider panel. The embossments, in some implementations, may be coveredwith a material such as a stretched tissue to mask the embossments.

A skilled artisan will understand that in certain cabin configurationsthe passengers seated immediately aft of the divider will be positionedsufficiently far away from the divider such that their heads will notimpact the divider during an emergency landing. In such configurationsthe energy absorbing zones can be omitted or rather included to providean additional measure of safety.

Turning to FIGS. 9D and 9E, in some implementations, a curved panelportion 942 of a contoured class divider 940 includes a series offlexible reversibly-jointed ribs 944 maintaining a convex profile of thecontoured class divider 940, as illustrated in FIG. 9D. The ribs, insome examples, may be designed using materials having sufficient tensilestrength and rigidity to withstand a load imposed by a large adultpassenger (e.g., up to 300 pounds). In some examples, the materials mayinclude titanium, aluminum, plastics. etc. However, upon a sufficientdynamic load impact such as a dynamic load created by passenger headimpact with the panel 942, the flexible reversibly-jointed ribs 944 mayreverse the convex jointed orientation. For example, as illustrated inFIG. 9E, the ribs 944 may reverse their joint orientation, causing thepanel 942 to warp to a concave orientation. In some embodiments, thepanel 942 may be designed using sufficiently flexible material to allowfor warping of the panel 942.

This embodiment provides the advantage that the divider may be movedentirely out of the range of the passengers' heads. Alternatively, thisapproach may be used in combination with an energy absorbing zone tominimize the extent and force of the impact with the passengers' heads.To further protect the passengers seated behind the contoured classdivider 940, in some embodiments, the flexible reversibly-jointed ribs944 may be designed to lock into and maintain the concave position uponimpact. For example, by preventing return to the convex orientation, thepassenger's heads may be spared a bounce-back impact by the ribs 944.

In some implementations, rather than depending upon a dynamic loadimpact to reverse the orientation of the reversibly-jointed ribs 944,the ribs may include a dynamic load trigger. In one example, a loadsensor built into the locking mechanism at the top of the contoureddivider panel may both release the contoured divider panel from itsrearward position and trigger reversal of the reversibly-jointed ribs944. In a particular example, a hinge 946 of each rib 944 may surroundan inflatable material such as an inflatable tube. By forcing air intothe inflatable tubes, for example, the hinge mechanism holding the ribsin the present orientation may be broken, causing the ribs to reverseorientation and thereby assume the concave orientation.

FIGS. 10A-10C illustrate alternative embodiments having known points ofimpact between the divider and the seats which permits determination ofload sharing and thereby permits “use” of the last inch of clearancebetween the divider and the seats. In some embodiments, a contouredclass divider panel includes one or more impact protrusions positionedon a fore surface of contoured class divider panel facing the seatbacksof the aft passenger seats such that at least one protrusion correspondsto each passenger seat back, providing known impact points between thecontoured class divider panel and the seat backs when the contouredclass divider panel contacts the passenger seats due to a strongdeceleration, e.g. above 10 g. The impact protrusions, for example, maybe used to provide predictable impact characteristics by identifyingknown localized impact points between the fore passenger seats and thecontoured class divider. Thus, the impact protrusions may simplifyimpact predictions in meeting regulation requirements for design of thecontoured class divider. This may be especially important in a contouredclass divider panel which remains nested closely to, if not abutting,the fore passenger seat backs. For example, by providing the impactprotrusions for load-sharing modeling purposes, a seating arrangementincluding a contoured class divider may be designed with a gap betweenthe contoured class divider and the fore passenger seat(s) of less thanabout one inch, or even less than one inch.

FIGS. 10A and 10C are aft perspective views of contoured class dividers1000, 1020 incorporating impact protrusions at approximately a shoulderheight of a passenger (e.g., below a headrest of the passenger seats1002). Turning to FIG. 10A, the contoured class divider 1000 includes aset of impact protrusions 1004 a, 1004 b, each impact protrusionpositioned behind a respective passenger seat 1002 a, 1002 b. In thismanner, a weight of material used to provide the impact protrusions 1004may be limited, and no impact protrusion will be visible through a gapthat may be between the passenger seats 1002 a, 1002 b. Turning to FIG.10C, the contoured class divider 1020 includes a single impactprotrusion 1022 positioned behind the passenger seats 1002. In thismanner, the installation may be simplified and a variety of seatingstyles may be used without concern for proper centering behind eachpassenger seat 1002. Although illustrated as a curved “speed bump” ofmaterial, in other implementations, the impact protrusions 1004, 1022may be designed as having a triangular cross section or rectangularcross section. In some implementations, the impact protrusions 1004,1022 are manufactured as part of the panel 1006, 1024 of the contouredclass divider 1000, 1020. In other implementations, the impactprotrusions 1004, 1022 are affixed to the panels 1006, 1024. Forexample, the impact protrusions 1004, 1022 can be made of materialshaving a strength sufficiently high to withstand the impact shockbetween the contoured class divider 1000, 1020 and the passenger seats1002, such as metallic alloys or high-density plastics. In otherembodiments, the impact protrusions are formed of energy absorbingmaterial such as rubber to reduce the peak load transferred between thedivider and the seats.

Alternatively, as illustrated in FIG. 10B, in some embodiments,passenger seats 1014 installed in front of a contoured class divider1010 may include one or more impact protrusions 1016 disposed to createa known contact surface with a panel 1012 of the contoured class divider1010. In this manner, the impact protrusions 1016 may be preciselypositioned upon each seat back.

In some embodiments, a number, depth, surface area, shape, materialcomposition, and/or positioning of each impact protrusion 1004, 1016,1022 may be selected to simplify impact simulations and/or to limitdamage caused by the impact between the contoured class divider 1000,1010, 1020 and the passenger seats 1002, 1014. For example, by disposingthe impact protrusion(s) 1004, 1022 upon the contoured class divider1000, 1020 (or, alternatively, protrusions 1016 on the passenger seats1014), a known point of impact is created between the passenger seats1002 (1014) and the contoured class divider 1000, 1020, (1010) thussimplifying calculations for load sharing in emergency circumstances.

In some implementations, each impact protrusion 1002, 1022 is disposedin a panel reinforced area of the fore surface of the contoured classdivider panel 1006, 1024 configured to withstand the impact shockbetween the contoured class divider 1000, 1020 and the passenger seats1002. The panel reinforced area can be made of a material having astrength higher than a material composing the panel 1000, 1020, e.g.high-density polyethylene, Delrin, steel alloy, acrylic, a thicknessgreater than a thickness of the panel 12, and/or a density greater thana density of the panel 12. Similarly, each impact protrusion 1016 may bedisposed in a passenger seat reinforced area of the aft surface of thepassenger seats 1014 of FIG. 10B.

Each impact protrusion 1002, 1016, 1022, in some implementations, iscoated with an energy absorbing layer to provide a damping between thecontoured class divider panel 1006, 1024, 1012, and the passenger seats1002, 1014. For example, the energy absorbing layer may limit scratchingand other damage to the contoured class divider panel 1006, 1024, 1012and/or the passenger seats 1002, 1014. The energy absorbing layer may bemade from elastic materials such as elastomer alloys, rubber alloys, orthe like.

One advantage of deploying the protrusions on the divider is that theseats need not be customized. The seats positioned directly in front ofthe divider may have the same configuration and construction as theremainder or majority of the seats in that cabin.

FIG. 11 is a side view of a contoured class divider 1100 affixed to atleast one passenger seat 1102 according to certain aspects of thedisclosure. The contoured class divider 1100 can be directly affixed tothe seat(s) 1102, for example, without affixing to a structure of thefloor of the cabin, such as an in-floor track. For example, thecontoured class divider 10 can at least one divider leg 1104 affixed toan aft part of a leg 1108 of the passenger seat 1102 via a fixationsystem 1106. The fixation system 1106 can include a bracket 1110 affixedto one end to the divider leg 1104 and to the other end to the leg 1108of the passenger seat 1102. Such an arrangement may require the dividerto pass the 16G dynamic test because it is mounted to a passengerrestraint system (the seat). However, this arrangement providesadditional ingress/egress foot clearance for the passengers seatedimmediately aft of the divider and may optimize usage of the spaceimmediately aft of the rear seat leg. Moreover, the use of theconnecting system to secure the top of the divider to the overhead binmay provide sufficient support such that the panel does not impartunacceptable additional load on the seat during an emergency landing.

Various details related to embodiments of contoured class dividers maybechanged without departing from the scope of the disclosure. Furthermore,the foregoing description of the preferred embodiments of the contouredclass divider and best mode for practicing the use of contoured classdividers as described herein are provided for the purpose ofillustration only and not for the purpose of limitation.

What is claimed is:
 1. A contoured class divider for dividing anaircraft cabin arrangement between at least one forward passenger seatand at least one aft passenger seat, the contoured class dividercomprising: a panel positioned adjacent to and rearwardly of the atleast one forward seat, the panel having a contoured shape for receivingthe back of the forward seat in at least one of a reclined position andan upright position, the panel extending substantially from an undersideof an overhead bin to a lower support assembly, wherein the lowersupport assembly supports a lower edge of the panel above a floor of theaircraft cabin such that passenger in the aft seat can stow luggagebeneath the forward seat; and means to articulate the panel from arearward position during normal operation to a forward position duringemergency landing.
 2. The contoured class divider of claim 1, whereinthe means to articulate includes a friction pin.
 3. The contoured classdivider of claim 1, wherein the means to articulate includes a springbiasing the divider into the forward or rearward position.
 4. Thecontoured class divider of claim 1, wherein the means to articulatearticulates the panel to the forward position when the panel issubjected to a dynamic load of greater than 16 G.
 5. The contoured classdivider of claim 1, wherein the lower support system includes at leastone pivot.
 6. The contoured class divider of claim 1, wherein the lowersupport system is mounted in a floor track of the cabin.
 7. Thecontoured class divider of claim 1, wherein the panel includes twosegments which pivot relative to one another.
 8. The contoured classdivider of claim 1, wherein the panel is located within one inch of theat least one forward passenger seat when the at least one forwardpassenger seat is in a take-off taxi and landing (TTOL) operationalposition.
 9. The contoured class divider of claim 1, wherein the panelincludes at least one means for mitigating head impact.
 10. Thecontoured class divider of claim 1, wherein the panel and the at leastone forward seat are configured to share loads during emergency landing.11. A method for dividing an aircraft cabin arrangement between at leastone forward passenger seat and at least one aft passenger seat, themethod comprising: positioning a panel of a contoured class divideradjacent to and rearwardly of the at least one forward seat, the panelhaving a contoured shape for receiving the back of the forward seat inat least one of a reclined position and an upright position; fixing alower support assembly of the contoured class divider to a structure ofa floor of the cabin, wherein the panel extends substantially from anunderside of an overhead bin to the lower support assembly, wherein thelower support assembly supports a lower edge of the panel above a floorof the aircraft cabin such that passenger in the aft seat can stowluggage beneath the forward seat; and connecting an upper edge of thepanel to an articulation mechanism, wherein the articulation mechanismcauses the panel to articulate during emergency landing from a rearwardposition used during normal operation to a forward position, and uponconnection, the panel extends substantially from an underside of anoverhead bin to the lower support assembly.
 12. The method of claim 11,wherein the upper edge of the panel is connected to the articulationmechanism via a friction pin extending upward from the upper edge of thepanel.
 13. The method of claim 11, wherein the articulation mechanism isconfigured to withstand deceleration of less than 16 G withoutarticulating the panel.
 14. The method of claim 11, wherein the lowersupport system includes at least one pivot.
 15. The method of claim 11,wherein the structure of the floor of the cabin is a floor track. 16.The method of claim 11, wherein positioning the panel comprisespositioning the panel in the rearward position within one inch of arecline position of the at least one forward passenger seat.
 17. Themethod of claim 11, wherein positioning the panel comprises positioningthe panel in the rearward position within a head impact zone of anaft-seated passenger in the at least one aft passenger seat, wherein thepanel comprises at least one head impact zone protection feature. 18.The method of claim 11, wherein the at least one head impact zoneprotection feature comprises energy absorbing material embedded in aportion of the panel within the head impact zone.
 19. The method ofclaim 11, wherein positioning the panel comprises positioning the panelsuch that, upon articulation, the panel is positioned to contact the atleast one forward seat.
 20. The method of claim 11, further comprising:prior to positioning the panel, removing a conventional class dividerfrom between the at least one forward passenger seat and the at leastone aft passenger seat; and relocating the at least one aft passengerseat at least 4 inches closer to the at least one forward passenger seatthan a seat mounting position for use with the conventional classdivider.